Abstract: An outlet tube arrangement for an aircraft nacelle may comprise a vent tube defining a vent tube outlet, the vent tube outlet configured to be flush with an outer surface of the aircraft nacelle, and an inner tube disposed within the vent tube, the inner tube configured to increase momentum of fluid flowing through the inner tube to urge the fluid to separate from the inner tube without wetting the aircraft nacelle upon exiting from the vent tube, wherein the inner tube comprises an inner tube inlet comprising an inlet cross-sectional area and an inner tube outlet comprising an outlet cross-sectional area, the inlet cross-sectional area being less than a cross-sectional area of the vent tube at the inner tube inlet, the inlet cross-sectional area being greater than the outlet cross-sectional area, and the inner tube outlet being flush with the vent tube outlet.

Abstract: An anti-icing system for annular turbofan engine housings what include a substantially closed annular housing at a leading edge of the turbofan engine housing, the annular housing containing a quantity of air and a conduit extending from a source of high pressure hot gas to the annular housing. The system also includes an injector connected to the end of the conduit and extending into the annular housing; one or more nozzles extending outwardly from the injector in a direction that the quantity of air circulates in the annular housing while the turbofan engine is operating. The nozzles have an entrance in fluid contact with the injector and an exit, wherein a cross-sectional area of the entrance is less than a cross-sectional area of the exit such that gas leaving the nozzles is travelling slower than gas entering the nozzles.

Abstract: A seal device that may be for a variable area fan nozzle (VAFN) assembly of a turbofan engine is positioned between first and second surfaces configured to move between close and distant positions. The seal device includes a first electrode engaged to the first surface and a second electrode spaced between the first and second surfaces and spaced from the first electrode. A resilient first element of the device is disposed between and engages to the first and second electrodes, and is configured to move between contracted and expanded states when the electrodes are energized. A resilient second element of the device opposes the second surface and is engaged to the second electrode. The second element is configured to move between a compressed mode when the first and second surfaces are in the close position and an extended mode when the first and second surfaces are in the distant position.

Abstract: An anti-icing system for annular gas turbine engine inlet housings includes a substantially closed annular housing at a leading edge of the gas turbine engine inlet housing, the annular housing containing a quantity of air and a conduit extending from a source of high-pressure hot bleed air to the annular housing. The system also includes an injector connected to the end of the conduit and extending into the annular housing and one or more nozzles extending outwardly from the injector in a direction that the quantity of air circulates in the annular housing. The system may include one or both of an airfoil on an upstream side of the injector and an air direction element disposed one the injector that causes the quantity of air to be directed toward an outlet of the one or more nozzles.

Abstract: An outlet tube arrangement for an aircraft nacelle may comprise a vent tube defining a vent tube outlet, the vent tube outlet configured to be flush with an outer surface of the aircraft nacelle, and an inner tube disposed within the vent tube, the inner tube configured to increase momentum of fluid flowing through the inner tube to urge the fluid to separate from the inner tube without wetting the aircraft nacelle upon exiting from the vent tube, wherein the inner tube comprises an inner tube inlet comprising an inlet cross-sectional area and an inner tube outlet comprising an outlet cross-sectional area, the inlet cross-sectional area being less than a cross-sectional area of the vent tube at the inner tube inlet, the inlet cross-sectional area being greater than the outlet cross-sectional area, and the inner tube outlet being flush with the vent tube outlet.

Abstract: Aspects of the disclosure are directed to a thrust reverser of an aircraft, comprising: a wall having a first surface that partially forms a flow channel associated with an air flow, a blocker door having a second surface that partially forms the flow channel, and a dielectric elastomeric device that is configured to selectively expand and contract within a cavity formed between the wall and the blocker door where the cavity is substantially radially adjacent to the flow channel when the thrust reverser is in a stowed state.

Abstract: A seal device that may be for a variable area fan nozzle (VAFN) assembly of a turbofan engine is positioned between first and second surfaces configured to move between close and distant positions. The seal device includes a first electrode engaged to the first surface and a second electrode spaced between the first and second surfaces and spaced from the first electrode. A resilient first element of the device is disposed between and engages to the first and second electrodes, and is configured to move between contracted and expanded states when the electrodes are energized. A resilient second element of the device opposes the second surface and is engaged to the second electrode. The second element is configured to move between a compressed mode when the first and second surfaces are in the close position and an extended mode when the first and second surfaces are in the distant position.

Abstract: An anti-icing system for annular gas turbine engine inlet housings includes a substantially closed annular housing at a leading edge of the gas turbine engine inlet housing, the annular housing containing a quantity of air and a conduit extending from a source of high-pressure hot bleed air to the annular housing. The system also includes an injector connected to the end of the conduit and extending into the annular housing and one or more nozzles extending outwardly from the injector in a direction that the quantity of air circulates in the annular housing. The system may include one or both of an airfoil on an upstream side of the injector and an air direction element disposed one the injector that causes the quantity of air to be directed toward an outlet of the one or more nozzles.

Abstract: An anti-icing system for annular turbofan engine housings what include a substantially closed annular housing at a leading edge of the turbofan engine housing, the annular housing containing a quantity of air and a conduit extending from a source of high pressure hot gas to the annular housing. The system also includes an injector connected to the end of the conduit and extending into the annular housing; one or more nozzles extending outwardly from the injector in a direction that the quantity of air circulates in the annular housing while the turbofan engine is operating. The nozzles have an entrance in fluid contact with the injector and an exit, wherein a cross-sectional area of the entrance is less than a cross-sectional area of the exit such that gas leaving the nozzles is travelling slower than gas entering the nozzles.

Abstract: Aspects of the disclosure are directed to a thrust reverser of an aircraft, comprising: a wall having a first surface that partially forms a flow channel associated with an air flow, a blocker door having a second surface that partially forms the flow channel, and a dielectric elastomeric device that is configured to selectively expand and contract within a cavity formed between the wall and the blocker door where the cavity is substantially radially adjacent to the flow channel when the thrust reverser is in a stowed state.

Abstract: A bleed air relief system for engines in which a flow of bleed air from the engine compressor is passed along a bleed air duct and exhausted into a bypass air stream passing through the engine. A cover is mounted over the outlet of the bleed air duct and can include flow passages and a diffuser for controlling the flow of bleed air being exhausted to enhance mixing of the bleed air with the bypass air stream.